Non-gyroscopic aeronautic engine.



W. P. HOLZMARK. NON-GYROSGOPIG ABRONAUTIG ENGINE.

APPLICATION FILED AUG. 26, 1912. 1,060,597, Patented May 6, 1913.

UNITED STATES PATENT OFFICE. 1

WILLIAM PHILLIP IIoLzMARzK, or -ST LOUIS, MISsoUIiI, ASSIGNOR or ONE-HALF 'ro Isaac HoLzivIAIiK, or ST. LOUIS, MISSOURI.

NoN-GYRoscoPI 'AiutoNau'IIc ENGINE.

.To Il 'ir-hom if may concern:

Be it.. known that I, IVILLIAM P. HOLZ-' MARK, a citizen of thelUnitedStates, and resident of St. Louis, Missouri, have invent-4 ed certain new and useful- Improvements in which the folloivingis a specification containing a full, clear, -and exact description,

reference being had to the accompanying drawings, forming a part hereof.

My invention relates toan improved nongyroscopic neronautc engine, and'consists in the novel construction hereinafter describedand designated in the [claims appended hereto.

Heretofore much trouble has been expe- 1' rienccd with aeronantic engines, in which all thefrevhluble parts move the saine direction during the operation of theenglne. The object ol my invention is tov provide y an improved -non-gyi'oseopie aeronautic enf' gine, in wln'cli a porti(` n'"Qf,the revoluble' parts rotate in reversedirections,as I have found by practical experience that. such an arrangement almost. if not fully, ob'viates' the gyrosf-opic action of the rotatingparts. In -thefdrawingsz Figure l is a sectional side elevation o t' :m engine having my invention apjljml'thereto.; 2.is a front elevation ofp'lhe'suh'e; and.Fig."3 is a. Sectional plan view ot' .the reversing gearused to connfectthe paris which rotate in reverse or opposite c'lirect'ions.

In carrying out `my invention I may make use of any cor'xrnon'form-,of cylinders and pistons, or any cominon form of rotary engine or rotatable cylinder engine, theonly necessary construction being two'engines or two varts of the same engine eared to rotate in opposite direction in or er to nulliy the gyroscopic action of the rot-ating parts.

In the present instance I lha've illustrated, my invention applied to a common 'four-A cycle engine. v

The numerals 1, 2, 3 and 4 respectively, indicate the cylinders ofY the'engine, the

same containing the usuallpistons connected.

Specification of Letters Patent. Application led'ugv'ust 26, 1912. Serial No. 717,123;

Patented May 6, 1913;

-and 4 are tobe driven. Thisreverse rotainto three sections, an intermediate section 7.

being connected to 'the outer sections by means of bevel gears 8 secured to the. adjoining ends of the sections by means of keys 9,

* or other common' means, and opposite beveled 'pinions 10 meshing with the teeth of both of the opposing gear wheels 8. One

,of the meeting endsof the shaft sections is preferably provided with abearing socket l1, in which is fitted a journal 12 projecting from the adjoining section and arranged to rotate in said bearing and thereby .be supported in lalinement. with the mating section (see Fig. 3). The Said pinions 10 are'each providedlwith a stub journal 13, upon which they Vmay freely rotate. The outer ends of said stub journals 13 are mounted in suitable bearings 14 supported upon the crank case pillars 15 while the inner ends of saidstub journals -are preferably fixed within the central block 16 which is located in the space between the opposing bevel ears Sand the opposing pinions .10, the sai block 16 being provided with a perforation 17. in which are loosely mounted-the mating shaft sections.

The numerali 18 indicates a common aeronautical propeller ixed 'u o n the end ofthe m'ain shaft, which projects through the crank case 19.

vOn the oppositeA projecting end voffthe` main shaft I have shown a common iiy wheel 20, but fin aeronautical engines the same will not be necessary, as it has been found that the rotating parts have sufficient momentum to enable a separate fly wheel to be dispensed with. l i The operation is as follows: Referring to Fig. 3it will be observed that the section 6 of the crank shaft will'rotate in the direc tion indicated by the arrow thereon, while the mating section 7 will -rotate in an oppo'- site orpreverse direction, also indicated by an arrow. This construction compels the cranks of the engines `land 4to rotate in a.

given direction, while the cranks of the adjoining engines 2 and 3 necessarily rotate in a reverse direction, butt-he power of all the -ioo engines will be simultaneously exerted to rotate the propeller 18 in the same direction in which the cranks of the engines 1 and 4 are rotated. The construction above described will also permit the explosions in the various cylinders to be balanced in a manner Well known to persons skilled in the art, and which need not therefore'be further described.

I claim:

l. A non-gyroscopic aeronauticfengine, comprising an engine provided with o positely rotatable axially-alined crank-s aft sections, and a reverse-gear connectin said sections to neutralize the gyroscopic e ect of each section.

2. The combination of two tandemaeronautical engines having axially alined crank-shaft sections, and a reverse-gear connecting said sections, to permit the crank of one'f said engines to rot-ate Vin one direction While thecrank-of the other engine rotates ina reverse direction.

3. The combination of' two aeronautical reversely-running engines having a series of axially-alined crank-shaft sections, suitable bearings for said sections, and. a reversinggear connecting said sect-ionsl and permitting one of said sections to rotate in one di WILLIAM PHIhLIl HOLZMARK.

Witnesses:

E. L. WALLACE, JOHN C.'H1cx oN'. 

